WO2016064455A2 - Dispositif d'atténuation de traînée - Google Patents

Dispositif d'atténuation de traînée Download PDF

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Publication number
WO2016064455A2
WO2016064455A2 PCT/US2015/041794 US2015041794W WO2016064455A2 WO 2016064455 A2 WO2016064455 A2 WO 2016064455A2 US 2015041794 W US2015041794 W US 2015041794W WO 2016064455 A2 WO2016064455 A2 WO 2016064455A2
Authority
WO
WIPO (PCT)
Prior art keywords
lipskin
cowl
mitigating
fasteners
mitigating device
Prior art date
Application number
PCT/US2015/041794
Other languages
English (en)
Other versions
WO2016064455A3 (fr
Inventor
Dennis Snyder
Wayne Duncan
Original Assignee
Shield Aerodynamics Llc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shield Aerodynamics Llc filed Critical Shield Aerodynamics Llc
Priority to US15/328,022 priority Critical patent/US10370113B2/en
Publication of WO2016064455A2 publication Critical patent/WO2016064455A2/fr
Publication of WO2016064455A3 publication Critical patent/WO2016064455A3/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B64C7/02—Nacelles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means

Definitions

  • the present invention relates to aircraft engines, more specifically to a nacelle, which can include an inlet area, a nose cowl area, and a fan cowl area for turbine engines, and a mitigation device to be fitted over a nacelle or other areas on an aircraft in order to reduce flow drag.
  • a nacelle which can include an inlet area, a nose cowl area, and a fan cowl area for turbine engines, and a mitigation device to be fitted over a nacelle or other areas on an aircraft in order to reduce flow drag.
  • parasitic drag which is composed of drag of various aerodynamic components.
  • skin friction drag is the drag on a body resulting from friction over its contact surfaces.
  • the flow in the boundary layer is entirely laminar or entirely turbulent over the surface.
  • the boundary layer is normally laminar near the leading edge of the object undergoing transition to a turbulent layer at some distance back along the surface.
  • gaps or joints such as at the interface between the lipskin and nose cowl and at the interface between the nose cowl the fan cowl.
  • nacelle lipskins that have been damaged and/or repaired. This is a common occurrence and introduces new drag potential.
  • nacelle friction drag has been approximated to account for 4-5% of the total friction drag of the aircraft, any reduction in nacelle friction drag causes a corresponding reduction in fuel consumption and aircraft operating costs. Thus, it is desirable to maintain laminar flow over as much of the nacelle surface as possible.
  • the present invention is directed to a system to mitigate flow drag and boundary layer separation over selected areas of the surface of an intake duct or nacelle or other areas of an aircraft by mitigating flow drag caused by interruptions in the surface of an aircraft intake or nacelle, such as, but not limited to, rivets, fasteners, joints, seams, cracks, and irregularities in surface smoothness.
  • the invention serves to mitigate flow drag and boundary layer separation over selected areas of the inner surface or throat of an intake duct or nacelle by mitigating flow drag and boundary separations caused by interruptions in the inner surface of an aircraft intake or nacelle, such as, but not limited to, rivets, fasteners, joints, seams, cracks, and irregularities in surface smoothness.
  • the invention serves to mitigate flow drag and boundary layer separation over selected areas of the inner surface of an intake duct or nacelle by mitigating flow drag caused by interruptions in the surface of an aircraft intake or nacelle, such as, but not limited to, rivets, fasteners, joints, seams, cracks, and irregularities in surface smoothness.
  • the invention can be adapted to the dimensions and curvatures of existing lipskins, to cover only the lipskin when damaged and to improve the aerodynamics of same where applicable, and/or to provide a replacement for the lipskin that may be a part of an extended segment that interfaces with the nose cowl or extends farther aft on the nacelle to interface with the fan cowl or beyond.
  • the invention serves to mitigate flow drag and boundary layer separation over selected areas of the surfaces of an intake duct or nacelle by mitigating flow drag caused by interruptions in the surfaces of an aircraft intake or nacelle, such as, but not limited to, rivets, fasteners, joints, seams, cracks, and irregularities in surface smoothness.
  • the invention has a design based on the dimensions and curvatures of an existing lipskin, such that potential drag from rows of rivets, fasteners, and joins can be mitigated by extending aft of the lipskin edge over the interface between the lipskin and the nose cowl.
  • the invention serves to mitigate flow drag and boundary layer separation over selected areas of the surface of an intake duct or nacelle by mitigating flow drag caused by interruptions in the surface of an aircraft intake or nacelle, such as, but not limited to, rivets, fasteners, joins, seams, cracks, and irregularities in surface smoothness, where the design of the device is based on the dimensions and curvatures of an existing lipskin.
  • the system in certain embodiments is capable of extending aft of the lipskin edge, over the interface between the lipskin and the nose cowl and fan cowl.
  • the system includes a means for airflow to be directed over the lipskin/nose cowl/fan cowl interface joints.
  • Certain embodiments of the present invention are directed to a system to
  • mitigate flow drag and boundary layer separation that further provides a low coefficient of friction surface and/or a self-cleaning surface and/or an acoustic-absorbing material and/or a means of de-icing and/or anti-icing, such as, but not limited to, a compressor bleed air inlet, an electronic or electric heating system, and/or an anti-icing material or coating.
  • Certain embodiments of the present invention are directed to a system to
  • mitigate flow drag and boundary layer separation that further provides a means for and method of attaching a forward material or object, such as but not limited to an engine protection device, to the nacelle.
  • FIG. 1 is a schematic representation of a side view example of nacelle elements that are known to cause flow drag.
  • FIG. 2 is a schematic representation of a side view of one preferred embodiment of the present invention.
  • FIG. 3 is a schematic representation of a perspective view of another preferred embodiment of the present invention illustrating the system unconnected to a nacelle's lipskin.
  • FIG. 4 is a schematic representation of a perspective view of another preferred embodiment of the present invention illustrating the system with a first connection to a nacelle's lipskin.
  • FIG. 5 is a schematic representation of a perspective view of another preferred embodiment of the present invention illustrating the system with a first connection to a nacelle's lipskin.
  • FIG. 6 is a schematic representation of a perspective view of another preferred embodiment of the present invention illustrating the system with a first connection to a nacelle's lipskin.
  • FIG. 7 is a schematic representation of a perspective view of one preferred embodiment
  • FIG. 8 is a schematic representation of a perspective view of one preferred embodiment
  • FIG. 9 is a schematic representation of a front perspective partial cut-away view of one embodiment of the present invention illustrating the outer and inner extended sleeves.
  • FIG. 10 is a schematic representation of a front perspective view of one preferred embodiment of the present invention illustrating the system's inner sleeve.
  • Fig. 1 shows a schematic representing an example of nacelle 1 segments (within square) that are known to cause flow drag, which includes the lipskin 2, the leading edge of the lipskin 3, the nose cowl 6, and the fan cowl 8. Rivets 5 are typically used to fasten the lipskin 2 to the nose cowl 6 and to fasten the nose cowl 6 to the fan cowl 8. Other fasteners are typically used to fasten the nose cowl 6 to the fan cowl 8 on the fan cowl 8 side of the interface of the two sections.
  • a joint 4 is caused by the interface of the lipskin 2 to the nose cowl 6 and the nose cowl 6 to the fan cowl 8.
  • a schematic representation shows a side view example of a joint 4 at the intersection of the aft end of the nose cowl 6 and the forward end of the fan cowl 8, within the nacelle section 1 .
  • the aft end of one preferred embodiment of the mitigating device 10 extends over and covers the section 13 of the surface of the nose cowl 6 up to a point that is just forward of the aft end of the nose cowl 6 and the forward of the fan cowl 8.
  • the air flow 9, beginning at the forward end of the nacelle 1 flows over one preferred embodiment of the mitigating device 10 and leaves the surface of the mitigating device 10 at an angle 1 1 which causes the air flow 9 to flow over the joint 4 and over the fastener 12 to mitigate drag caused by the fastener 12 and the joint 4. Airflow 1 1 continues over the uncovered section 14 of the fan cowl 8.
  • a schematic representation shows a perspective view of a preferred embodiment of the mitigating device 10 positioned away (for clarity) from the lipskin 2, the nose cowl 6, the fan cowl 8, and the thrust reverser 18.
  • the joints 4, 4a, 4b are at the interface of each of those sections.
  • Fig. 4 shows a schematic representation of a perspective view of a preferred embodiment of the mitigating device 10 having the first connection to lipskin 2 to mitigate drag that can be caused by a damaged lipskin 2 or to improve the aerodynamic shape or surface of lipskin 2. Any such drag will in turn affect the airflow over nose cowl 6, fan cowl 8, and thrust reverser 18.
  • the mitigating device 10 does not extend over the aft edge of lipskin 2 or over joint 4.
  • FIG. 5 shows a schematic representation of a perspective view of a preferred embodiment
  • mitigating device 10 having a first connection to lipskin 2, extending over the aft edge of lipskin 2, and continuing over the leading edge of nose cowl 6.
  • This embodiment mitigates drag that can be caused by rivets (not shown) in the aft edge of the lipskin 2 and rivets in the forward edge of nose cowl 6.
  • this embodiment of the mitigating device 10 covers or mitigates drag that can be caused by the joint 4 between lipskin 2 and nose cowl 6.
  • the mitigating device 10 is capable of mitigating drag caused by lipskin 2, nose cowl 6, and join 4, promoting the continuation of laminar flow over fan cowl 8 and thrust reverser 18.
  • the inner sleeve of mitigating device 10 is shown extending into the nacelle over the edge of lipskin 2 to mitigate drag from the inner rivets (not shown) and the inner interface joint 4 at the connection of lipskin 2 and nose cowl 6.
  • FIG. 6 Another embodiment of the mitigating system is shown in Fig. 6. In this
  • the mitigating device 10 has a first connection at lipskin 2, extends over the aft edge of lipskin 2, and continues over the leading edge of nose cowl 6. The mitigating device 10 continues farther to the aft edge of nose cowl 6 just forward of the joint 4 and the fan cowl 8. In this embodiment the mitigating device 10 mitigates drag that can be caused by rivets (not shown) in the aft edge of lipskin 2, at the forward edge of nose cowl 6, and at the aft edge of nose cowl 6. Additionally, the mitigating device 10 covers or mitigates drag that can be caused by the joint 4 between lipskin 2 and nose cowl 6.
  • the mitigating device 10 is also capable of mitigating drag caused by joint 4a between nose cowl 6 and fan cowl 8 by providing means for air flow to avoid contact with joint 4a and fasteners 7, which extend circumferentially about the surface of the leading edge of fan cowl 8.
  • the inner sleeve of the mitigating device 10 is shown extending into the nacelle over the edge of lipskin 2 in order to mitigate drag from the inner rivets (not shown) and the inner interface joint 4 at the connection of lipskin 2 and nose cowl 6.
  • FIG. 7 represents a perspective view of a preferred embodiment of the mitigating device 10 with separate outer 19 and inner 20 sleeves.
  • the outer sleeves 19 and inner sleeves 20 are capable of being separately extended to any desired length.
  • the inner sleeve 20 can be extended to cover potential boundary layer separations caused by rivets and seams, such as, but not limited to, the inner-nacelle interface where the lipskin is joined to the nose cowl by rivets within the inner nacelle throat.
  • either or both sleeves can contain or be coated or covered with specific materials, such as, but not limited to, acoustic absorbing materials.
  • FIG. 8 shows a schematic representation of a perspective view of a preferred embodiment of the mitigating device 10 with an outside material or device 21 attached mechanically or non-mechanically to the leading edge of the mitigating device 10, which is attached to nacelle 1 .
  • mitigating system 10 with an extended inner sleeve 20, which reduces drag and boundary layer separation caused by rivets 5a and the intersection 4b of the lipskin 2 and the nose cowl 6.
  • the mitigating system 10 may also extend farther into the throat of the nacelle to mitigate flow drag and boundary layer separation from irregular or non- flush inner surface interfaces.
  • the outer sleeve 19 extends over the rearward section of the lipskin 2, covering the forward-most rivets 5, and extends over the intersection 4, with the nose cowl 6 and further extends to cover the outer rivets 5 in the rearward section of nose cowl 6, and extending to a position forward of the intersection 4a of nose cowl 6 and fan cowl 8.
  • mitigating device 10 may be connected by adhesives or other means.
  • FIG. 10 An additional embodiment of the mitigating system is shown in Fig. 10. This
  • the mitigating system 10 may also extend farther into the throat of the nacelle to mitigate flow drag and boundary layer separation from irregular or non-flush inner surface interfaces.
  • the mitigating device 10 can extend
  • the mitigating device 10 is also capable of being interfaced into a nacelle, as a part or as the complete nacelle, such as, but not limited to, in an original equipment system. Still another embodiment of the mitigating device 10 can be used to replace an existing lipskin or can be used as a new lipskin where a current lipskin does not exist, such as, but not limited to, in an original equipment system. This lipskin system can interface with the nose cowl or be extended to interface with the fan cowl, or can be extended further to interface with the thrust reverser section.
  • the mitigating system in one embodiment, further comprises a thrust reverser section.
  • the mitigating system is also capable of being retrofitted for existing aircraft or may be interfaced into a nacelle, as part or as the complete nacelle.
  • the mitigating device is also capable of being a nacelle inlet protective cover that is conformed to the existing lipskin and elongated to provide means to mitigate drag and boundary layer separations arising from the interface of the lipskin and nose cowl and/or the interface of the nose cowl and the fan cowl and/or the interface of the fan cowl and thrust reverser section.
  • the mitigating system in any of the embodiments described herein is capable of being constructed of differing high strength-to-weight materials, such as, but not limited to, metals, metal alloys and/or powders, and composites and/or polymer materials.
  • the mitigating device may be used in applications other than along the lipskin of engine nacelles, such as to cover other areas of aircraft that produce drag, including, for example, bulges along the fuselage or wings for antennas or other equipment, or along leadings edges such as wings, stabilizers, winglets, and canards.
  • the mitigating device may be used as original equipment, as an add-on device to improve laminar flow, or as a means to cover a damaged area on an aircraft.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un système d'atténuation permettant de réduire la traînée dans des moteurs d'avion qui utilise un dispositif d'atténuation fixé soit à la nacelle d'un moteur pour atténuer la traînée de l'écoulement d'air se déplaçant à travers la nacelle. Le dispositif d'atténuation possède un manchon interne et un manchon externe, chacun pouvant être réglé séparément de manière à s'étendre sur toute longueur souhaitée à travers la surface interne ou la surface externe de la nacelle. Au fur et à mesure que les manchons sont étendus, ils recouvrent un plus grand nombre d'éléments de traînée, ce qui permet d'améliorer les propriétés aérodynamiques du moteur d'avion.
PCT/US2015/041794 2014-07-23 2015-07-23 Dispositif d'atténuation de traînée WO2016064455A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US15/328,022 US10370113B2 (en) 2014-07-23 2015-07-23 Flow drag mitigation device

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201462027972P 2014-07-23 2014-07-23
US62/027,972 2014-07-23

Publications (2)

Publication Number Publication Date
WO2016064455A2 true WO2016064455A2 (fr) 2016-04-28
WO2016064455A3 WO2016064455A3 (fr) 2016-07-28

Family

ID=55761732

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2015/041794 WO2016064455A2 (fr) 2014-07-23 2015-07-23 Dispositif d'atténuation de traînée

Country Status (2)

Country Link
US (1) US10370113B2 (fr)
WO (1) WO2016064455A2 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3027624B1 (fr) * 2014-10-27 2019-04-19 Safran Aircraft Engines Circuit de degivrage d'une levre d'entree d'air d'un ensemble propulsif d'aeronef
GB201811422D0 (en) * 2018-07-12 2018-08-29 Rolls Royce Plc Low drag surface

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9424495D0 (en) 1994-12-05 1995-01-25 Short Brothers Plc Aerodynamic low drag structure
FR2757823B1 (fr) * 1996-12-26 1999-03-12 Aerospatiale Nacelle de turboreacteur a ecoulement laminaire
US5915403A (en) 1998-04-14 1999-06-29 The Boeing Company Biplanar scarfed nacelle inlet
US7469862B2 (en) * 2005-04-22 2008-12-30 Goodrich Corporation Aircraft engine nacelle inlet having access opening for electrical ice protection system
US7721525B2 (en) 2006-07-19 2010-05-25 Rohr, Inc. Aircraft engine inlet having zone of deformation
US9169779B2 (en) 2007-10-09 2015-10-27 United Technologies Corp. Systems and methods for altering inlet airflow of gas turbine engines
US8752795B2 (en) * 2010-11-23 2014-06-17 John Ralph Stewart, III Inlet nose cowl with a locally thickened fastening portion to enable an uninterrupted airflow surface

Also Published As

Publication number Publication date
US10370113B2 (en) 2019-08-06
US20170190437A1 (en) 2017-07-06
WO2016064455A3 (fr) 2016-07-28

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